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EP2322765B1 - Membre annulaire pour moteur à turbine à gaz à double flux - Google Patents

Membre annulaire pour moteur à turbine à gaz à double flux Download PDF

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Publication number
EP2322765B1
EP2322765B1 EP10186876.8A EP10186876A EP2322765B1 EP 2322765 B1 EP2322765 B1 EP 2322765B1 EP 10186876 A EP10186876 A EP 10186876A EP 2322765 B1 EP2322765 B1 EP 2322765B1
Authority
EP
European Patent Office
Prior art keywords
hook
hook member
annulus filler
rotor disc
filler
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP10186876.8A
Other languages
German (de)
English (en)
Other versions
EP2322765A2 (fr
EP2322765A3 (fr
Inventor
Matthew Hoyland
Paul Mason
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP2322765A2 publication Critical patent/EP2322765A2/fr
Publication of EP2322765A3 publication Critical patent/EP2322765A3/fr
Application granted granted Critical
Publication of EP2322765B1 publication Critical patent/EP2322765B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods

Definitions

  • the present invention relates to annulus fillers for bridging gaps between adjacent blades of a gas turbine engine stage.
  • the fan stage of a gas turbine engine comprises a plurality of radially extending fan blades mounted on a rotor or fan disc.
  • the blades are mounted on the disc by inserting a root portion of the blade in a complementary retention groove in the outer face of the disc periphery.
  • annulus fillers are used to bridge the spaces between adjacent blades.
  • seals between the annulus fillers and the adjacent fan blades are also provided by resilient strips bonded to the annulus fillers adjacent the fan blades.
  • the fillers may be manufactured from relatively lightweight materials and, in the event of damage, may be replaced independently of the blades.
  • annulus fillers with features for removably attaching them to the rotor disc.
  • annulus fillers can be provided with axially spaced hook members, the hook members sliding into engagement with respective parts of the rotor disc.
  • Figure 1 shows an example of such an annulus filler viewed from the side
  • Figure 2 shows the annulus filler fitted to the rotor disc as viewed in transverse cross-section.
  • Document US 2009/0208335 A1 discloses another example of such an annulus filler.
  • the upper surface or lid 2 of the annulus filler 1 bridges the gap between two adjacent fan blades 3 (one of which is shown in outline in Figure 2 ) and defines the inner wall of the flow annulus of a fan stage.
  • the annulus filler 1 is mounted on a fan disc 4 by two hook members 5, 6 respectively towards the forward and rearward ends of the annulus filler 1.
  • the hook members are configured to engage with outwardly directed hooks provided on the fan disc 4.
  • the annulus filler is also attached to a support ring 7 by a retention flange 8 provided at the forward end of the annulus filler.
  • the annulus filler is provided with a rear lip 9 which is configured to fit under a rear fan seal 10 located axially behind the rotor disc 4 to limit deflection under running conditions.
  • the front edge of the annulus filler defines a front lip 11 which is configured to fit under a spinner fairing 12 or nose cone located axially ahead of the annulus filler.
  • the two opposed side faces 13, 14 of the annulus filler are provided with respective seal strips (not shown) and confront the aerofoil surfaces of the adjacent fan blades 3 in a sealing manner.
  • the retention flange 8 carries a forwardly extending spigot or pin 15.
  • the spigot or pin 15 is arranged for engagement within a corresponding aperture or recess provided in the support ring 7.
  • the retention flange can also be provided with a mounting aperture (not shown) which is arranged for co-alignment with a corresponding mounting aperture (not shown) provided through the support ring 7.
  • the co-aligned mounting apertures are sized to receive a mounting bolt.
  • the hook members 5, 6 define respective arcuate channels 16, 17.
  • the channels are curved in such a manner as to be centred on the rotational axis of the engine (not shown), and cooperate with a correspondingly arcuate hooks 18, 19 on the rotor disc 4.
  • the present invention provides an annulus filler for mounting to a rotor disc of a gas turbine engine as set forth in claim 1.
  • the forward hook member may have a stop surface which, on engaging the forward hook member to the forward outwardly directed hook, can abut a surface of the rotor disc to prevent or reduce rotation of the annulus filler about the forward hook member, whereby the forward hook member can only engage with the forward outwardly directed hook when the rearward hook member also engages with the rearward outwardly directed hook.
  • annulus filler for mounting to a rotor disc of a gas turbine engine, the annulus filler comprising: a lid for bridging the gap between two adjacent blades attached to the rotor disc, and forward and rearward hook members projecting below the lid and configured to respectively engage with forward and rearward outwardly directed hooks provided on the rotor disc when the annulus filler is translated in a generally rearwards direction on mounting of the annulus filler to the rotor disc; wherein the forward hook member has a stop surface which, on engaging the forward hook member to the forward outwardly directed hook, can abut a surface of the rotor disc to prevent or reduce rotation of the annulus filler about the forward hook member, whereby the forward hook member can only engage with the forward outwardly directed hook when the rearward hook member also engages with the rearward outwardly directed hook.
  • the annulus filler may have any one or, to the extent that they are compatible, any combination of the following optional features.
  • annulus filler When the annulus filler has a stop surface, this may conveniently be provided by a protuberance on a front-facing side of the forward hook member.
  • the lid has a stiffening rib on the underside thereof, the rib extending between the forward and rearward hook members.
  • the stiffening rib can help to prevent deflections of the lid between the forward and rearward hook members.
  • the rib can help the forward hook member to only engage with the forward outwardly directed hook when the rearward hook member also engages with the rearward outwardly directed hook.
  • the conventional annulus filler shown in Figures 1 and 2 can be misassembled with the rotor. This can lead to the release of the filler and an aborted take-off. The released filler can also cause significant damage to the fan case and/or fan liners.
  • FIG. 3 is a transverse cross-section of an annulus filler 1 incorrectly fitted to a rotor disc.
  • the flexibility of the forward end of the filler and of the support ring 7 allow the support ring to be installed, giving the appearance of a correctly fitted filler. However, without the engagement of the rear hook member, the filler will be released when the engine is started.
  • the rear lip 9 of the filler can ride above the rear fan seal 10 during filler installation.
  • the high centrifugal loads experienced by the filler can cause large deflections and ultimately lead to filler failure.
  • Figure 4 shows (a) a side view of the rear end and (b) a perspective view of the rear end of an annulus filler 101 according to an embodiment of the present invention
  • Figure 5 shows (a) a side view of the front end and (b) a perspective view of the underside of the front end of the annulus filler
  • Figure 6 shows a transverse cross-section of the annulus filler in an attempt to incorrectly fit the filler to a rotor disc.
  • the filler 101 has a lid 102 which bridges the gap between two adjacent fan blades (not shown) attached to rotor disc 104.
  • Forward 105 and rearward 106 hook members extend down from the underside of the lid.
  • the hook members engage with corresponding forward 118 and rearward 119 hooks extending outwardly from rotor disc 104.
  • Front 111 and rear 109 lips respectively extend from the front and rear edges of the lid.
  • the front lip fits under a nose cone 112 located forward of the annulus filler and the rear lip fits under a rear fan seal 110 located rearward of the annulus filler.
  • the positions and purposes of the hook members and lips are thus similar to those of the corresponding features of the conventional filler shown in Figures 1 and 2 .
  • two spaced guide ramps 120 extend downwardly at an angle from the rear edge of the rear lip.
  • the angle of the ramps encourages the rear lip to slide under the rear fan seal when the filler 101 is translated in a generally rearwards direction on mounting of the filler to the rotor disc 104. In this way, the problem of the rear lip riding above the rear fan seal can be avoided, even on blind assembly.
  • the ramps can be particularly effective on module build when the entire rotating fan module (i.e. disc, fan blades and annulus fillers) is assembled to the fan shaft and rear fan seal.
  • the relatively short lengths of the ramps relative to the length of the rear lip help to reduce the additional weight of the ramps.
  • a further advantage of the guide ramps is that they provide additional length to the rear lip. During surge the fan rear seal can translate axially forwards and rearwards, creating potential for it to become disengaged from the filler. The extra length provided by the guide ramps reduces the likelihood of such disengagement.
  • a tab or protuberance 121 is provided at front-facing side of the forward hook member 105.
  • the tab provides a stop surface 122 which on engagement of the forward hook member to the forward outwardly directed hook 118, can abut a surface 123 of the rotor disc. As shown in Figure 6 , this abutment helps to reduce rotation of the filler about the forward hook member.
  • the only very limited rotation about the forward hook member which is now possible sets up a clash between the rearward hook member and the rearward outwardly directed hook, preventing the rearward hook member riding above the rearward outwardly directed hook and also preventing the forward hook member engaging with the forward outwardly directed hook.
  • the forward hook member can only engage with the forward outwardly directed hook when there is little or no rotation and the rearward hook member also engages with the rearwardly outwardly directed hook.
  • a pair of spaced stiffening ribs 124 extend between the forward 105 and rearward 106 hook members on the underside of the lid 102.
  • the ribs reduce deflection of the lid and preserve the relative positions of the forward and rearward hook members. This therefore also helps to prevent the rearward hook member riding above the rearward outwardly directed hook.
  • the guide ramps 120 and the tab 121 can prevent misassembly of the filler 101 and therefore prevent filler release and associated aborted take offs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (4)

  1. Élément de remplissage annulaire (1) destiné à être monté sur un disque de rotor (4) d'un moteur à turbine à gaz et comblant l'espace entre des pales de soufflante adjacentes (3) et des premier et second éléments lavés au gaz (112, 110) d'un étage de moteur à turbine, le disque de rotor ayant un premier crochet (18, 118) de disque de rotor et un second crochet (19, 119) de disque de rotor, l'élément de remplissage annulaire (1) comprenant :
    un couvercle (2) ayant une extrémité avant et une extrémité arrière ;
    un premier élément de crochet (5, 105) faisant saillie du couvercle de façon adjacente à l'extrémité avant de celui-ci et configuré pour s'engager dans le premier crochet (18, 118) de disque de rotor du disque de rotor (4) ;
    un second élément de crochet (6, 106) faisant saillie du couvercle de façon adjacente à l'extrémité arrière de celui-ci et configuré pour s'engager dans le second crochet (19, 119) de disque de rotor du disque de rotor (4) ;
    une première lèvre (11, 111) s'étendant de l'extrémité avant du couvercle et étant configurée pour s'agencer sous le premier élément lavé au gaz (112) du moteur à turbine à gaz ; et
    une seconde lèvre (9, 109) s'étendant de l'extrémité arrière du couvercle et étant configurée pour s'agencer sous le second élément lavé au gaz (10, 110) du moteur à turbine à gaz ;
    caractérisé en ce que l'élément de remplissage annulaire comprend en outre une ou plusieurs rampes de guidage (120) qui s'étendent de la seconde lèvre (9, 109), la ou chaque rampe de guidage ayant une inclinaison dans une direction vers les premier et second éléments de crochet par rapport à la seconde lèvre pour favoriser l'agencement de la seconde lèvre sous le second élément lavé au gaz (110) lorsque l'élément de remplissage annulaire est translaté dans une direction vers ledit second élément lavé au gaz.
  2. Élément de remplissage annulaire selon la revendication 1, dans lequel le premier élément de crochet (5, 105) a une surface d'arrêt (122) qui, lorsqu'on engage le premier élément de crochet dans le premier crochet de disque de rotor, est configurée pour venir en butée contre une surface (123) du disque de rotor pour empêcher ou réduire la rotation de l'élément de remplissage annulaire autour du premier élément de crochet.
  3. Élément de remplissage annulaire selon la revendication 2, dans lequel la surface d'arrêt (122) est fournie par une protubérance sur un côté du premier élément de crochet faisant face vers l'extrémité avant du couvercle.
  4. Élément de remplissage annulaire selon l'une quelconque des revendications précédentes, dans lequel le couvercle a une nervure de raidissement (124) qui s'étend entre le premier élément de crochet (5, 105) et le second élément de crochet (6, 106).
EP10186876.8A 2009-11-11 2010-10-07 Membre annulaire pour moteur à turbine à gaz à double flux Not-in-force EP2322765B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0919657.7A GB0919657D0 (en) 2009-11-11 2009-11-11 Annulus filler for a gas turbine engine
GBGB1003442.9A GB201003442D0 (en) 2009-11-11 2010-03-02 Annulus filler for a gas turbine engine

Publications (3)

Publication Number Publication Date
EP2322765A2 EP2322765A2 (fr) 2011-05-18
EP2322765A3 EP2322765A3 (fr) 2017-10-11
EP2322765B1 true EP2322765B1 (fr) 2018-08-29

Family

ID=41502150

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10186876.8A Not-in-force EP2322765B1 (fr) 2009-11-11 2010-10-07 Membre annulaire pour moteur à turbine à gaz à double flux

Country Status (3)

Country Link
US (1) US8814521B2 (fr)
EP (1) EP2322765B1 (fr)
GB (2) GB0919657D0 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
FR3145583A1 (fr) * 2023-02-06 2024-08-09 Safran Aircraft Engines Ensemble de rotor à plateformes indépendantes et procédé de montage d’un tel rotor

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2971552B1 (fr) * 2013-03-15 2020-09-23 United Technologies Corporation Plateforme de ventilateur composite moulée par injection
GB201400756D0 (en) * 2014-01-16 2014-03-05 Rolls Royce Plc Blisk
US10156151B2 (en) 2014-10-23 2018-12-18 Rolls-Royce North American Technologies Inc. Composite annulus filler
US12421860B2 (en) * 2023-04-27 2025-09-23 Rolls-Royce Plc Annulus filler for a gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9208409D0 (en) 1992-04-16 1992-06-03 Rolls Royce Plc Rotors for gas turbine engines
GB9828484D0 (en) 1998-12-24 1999-02-17 Rolls Royce Plc Improvements in or relating to bladed structures for fluid flow propulsion engines
GB0802834D0 (en) 2008-02-18 2008-03-26 Rolls Royce Plc Annulus filler
GB0804260D0 (en) 2008-03-07 2008-04-16 Rolls Royce Plc Annulus filler

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
FR3145583A1 (fr) * 2023-02-06 2024-08-09 Safran Aircraft Engines Ensemble de rotor à plateformes indépendantes et procédé de montage d’un tel rotor
WO2024165807A1 (fr) * 2023-02-06 2024-08-15 Safran Aircraft Engines Ensemble de rotor à plateformes indépendantes et procédé de montage d'un tel rotor

Also Published As

Publication number Publication date
US8814521B2 (en) 2014-08-26
EP2322765A2 (fr) 2011-05-18
US20110110780A1 (en) 2011-05-12
GB0919657D0 (en) 2009-12-23
GB201003442D0 (en) 2010-04-14
EP2322765A3 (fr) 2017-10-11

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